EP1185456A1 - Einrichtung zum gleichzeitigen verriegeln mehrerer aktuatoren - Google Patents
Einrichtung zum gleichzeitigen verriegeln mehrerer aktuatorenInfo
- Publication number
- EP1185456A1 EP1185456A1 EP00936856A EP00936856A EP1185456A1 EP 1185456 A1 EP1185456 A1 EP 1185456A1 EP 00936856 A EP00936856 A EP 00936856A EP 00936856 A EP00936856 A EP 00936856A EP 1185456 A1 EP1185456 A1 EP 1185456A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- locking
- locking elements
- actuators
- elements
- actuator
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000006073 displacement reaction Methods 0.000 claims 1
- 210000000078 claw Anatomy 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000013459 approach Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/72—Means acting on blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/30—Wing lift efficiency
Definitions
- the invention relates to a device for the simultaneous locking of several actuators with the features according to the preamble of claim 1.
- actuators are used that are brought into a safe position and locked there when the power supply fails or is switched off. It is known to provide Götte, HJ: "Single blade control for helicopters using servo-hydraulic actuators in the rotor head", 11th Aachen Fluid Power Colloquium, Hydraulics Department, Aachen 1994, to provide safety pistons for helicopters with actuators for individual control of the rotor blades return to a safe position and hold it there.
- the safety pistons have a conically shaped end which engages in a wedge-shaped annular groove in the actuator piston.
- the actuator is actuated hydraulically, the hydraulic pressure acting on the conical ends of the securing pistons and pushing them against the force of a spring into a release position for the actuator piston. If the hydraulic pressure fails, the springs, which can be gas storage springs, push the safety pistons back into the wedge-shaped groove and lock the actuating piston without play.
- a separate locking device with an actuating mechanism is provided for each actuator.
- the invention has for its object to provide a device for the simultaneous locking of several actuators, which is also suitable for use with electrically or electromagnetically actuated actuators, and which requires relatively little energy and space.
- This object is achieved according to the invention by the features of claim 1. Further refinements result from the subclaims.
- a plurality of second locking elements are connected to one another. They are operated by a common device. Depending on the number of interlocking locking elements, a corresponding number is eliminated
- Actuators so that the number of components required is greatly reduced. This also reduces the security risk, which is of great importance in helicopter applications. In addition, the weight and construction costs are reduced.
- connection of the second locking elements to one another is particularly simple if all locking elements are arranged in one plane.
- This plane can be a longitudinal plane or a transverse plane.
- the first locking elements and / or the actuators are expediently each arranged in the same plane, so that over supporting elements to bridge the distances of different levels can be avoided.
- the use of the device according to the invention in helicopters is particularly advantageous.
- the security risk, the weight and the masses play a decisive role in the rotating system.
- several actuators are usually required in the rotating system, which must be brought into a safe position and locked at the same time in the event of a power supply failure in order to be able to navigate the helicopter mechanically safely.
- the actuators expediently act on the control system of the rotor blades via a mixing lever.
- the mixing levers are housed in the rotor mast and have three articulation axes, namely one for the actuator, one for the control rod of the mechanical control and one for a control rod leading to a blade horn.
- the first locking elements are advantageously arranged in the region of the articulation axis of the actuator on the mixing lever and connected to it. If the first locking element is locked by the second locking element, the individual control of the rotor blades is blocked by the actuator. Then only the mechanical control works.
- the first and second locking elements are expediently arranged in a plane of rotation of the rotor mast, it being possible for the second locking elements to be connected to one another via a locking ring or a star-shaped element.
- locking elements can be formed by wedge-shaped recesses in the locking ring into which the first locking elements place the locking ring or the star-shaped element engage.
- the locking ring or the star-shaped element is rotated by an auxiliary force against the force of a spring into an unlocking position in which the first locking element is freely movable at least within predetermined limits in the actuating direction of the actuator.
- the prestressed spring rotates the locking ring or the star-shaped element back into the locking position, so that the first locking elements are locked in a safe position.
- the locking ring or the connecting part of the second locking elements it is also possible for the locking ring or the connecting part of the second locking elements to perform an axial movement for locking the first locking elements if the locking elements are designed or arranged accordingly.
- Game and position tolerances can lead to problems if several actuators are arranged on a locking ring. These can be compensated for in a reliable manner in that either the first or the second locking elements are designed to be resilient and pre-tensioned. This prevents jamming when locking and guarantees freedom of play when locked.
- FIG. 1 is a schematic partial longitudinal section through a rotor mast of a helicopter
- Fig. 3 shows a section through the locking mechanism along the line III-III in Fig. 1 and
- Fig. 4 shows a partial section of an embodiment of a
- FIG. 5 is a top view of the configuration of a locking element according to FIG. 4.
- a piston rod 2 acts on the articulation axis 8 as an actuator of an actuator 1, while a mechanical control linkage (not shown in more detail) for navigating the helicopter acts on the articulation axis 10 at the other end of the mixing lever 7.
- the control signals of the actuator 1 and the mechanical control linkage are transmitted to the associated rotor blade of the helicopter via a control rod.
- the control rod engages on the third articulation axis 9 of the mixing lever 7.
- a device 3 for simultaneous locking of the actuators 1 contains first locking elements 5 and second locking elements 6.
- the first locking element 5 is firmly connected to the mixing lever 7. It engages in the second locking element 6, which is fixed in an adjusting direction 15 of the actuator 1 in the rotor mast 4.
- the second locking element 6 consists of a wedge-shaped recess 12 of a locking ring 11, in which the first locking element 5 engages.
- the wedge shape means that it is centered and locked at the end of the adjustment movement in the locking direction between the wedge surfaces without play.
- the first locking element has a first wedge element 16 and a second wedge element 17.
- the first wedge element is coupled to the mixing lever 7 via the claw 20 on the articulation axis 8 with respect to the direction of movement of the piston rod 2.
- the second wedge element 17 can be displaced relative to the first wedge element 16 along a dovetail guide 21.
- a plate spring 18 is arranged, which is biased by the screw 19. Exceeds the pressure force acting on the plate spring 18, the biasing force generated by the screw 19 z. B. when locking, the displaceable second wedge element 17 approaches the fixed first wedge element 16.
- the inherently preloaded wedge element 5 is thus resilient when the biasing force is exceeded.
- play and position tolerances between the first and second locking elements 5, 6 are compensated for by the resilient design. With this configuration, even with different engagement positions complete locking of all actuators is ensured.
- the second wedge elements 6 are designed to be resilient.
- the locking ring 11 can be rotated in the adjusting direction 14 by a given angle of rotation. To unlock the actuator 1, it is brought into the unlocking position by means of an auxiliary force against the force of a spring, in which the first locking element 5 can move freely at least to a limited extent in the adjustment direction 15 of the actuator 1. If the power supply is switched off or fails, the locking ring 11 is turned back by the spring force into the locking position in which the first locking element 5 rests on the flanks of the wedge-shaped recess 12 without play and is therefore blocked with the coupled piston rod 2 in the direction of adjustment 15 .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
- Transmission Devices (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19926429 | 1999-06-10 | ||
DE19926429A DE19926429A1 (de) | 1999-06-10 | 1999-06-10 | Einrichtung zum gleichzeitigen Verriegeln mehrerer Aktuatoren |
PCT/EP2000/005070 WO2000076844A1 (de) | 1999-06-10 | 2000-06-03 | Einrichtung zum gleichzeitigen verriegeln mehrerer aktuatoren |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1185456A1 true EP1185456A1 (de) | 2002-03-13 |
EP1185456B1 EP1185456B1 (de) | 2004-02-04 |
Family
ID=7910768
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP00936856A Expired - Lifetime EP1185456B1 (de) | 1999-06-10 | 2000-06-03 | Einrichtung zum gleichzeitigen verriegeln mehrerer aktuatoren |
Country Status (4)
Country | Link |
---|---|
US (1) | US6676377B1 (de) |
EP (1) | EP1185456B1 (de) |
DE (2) | DE19926429A1 (de) |
WO (1) | WO2000076844A1 (de) |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE10125178B4 (de) * | 2001-05-23 | 2010-01-28 | Zf Luftfahrttechnik Gmbh | Individuelle Rotorblatt-Steuerungsvorrichtung |
WO2012024677A2 (en) | 2010-08-20 | 2012-02-23 | Redviking Group, Llc | Transmission test system |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB760646A (en) | 1953-09-02 | 1956-11-07 | De Long Corp | Improved perforated caisson jack assembly |
FR2460435A1 (fr) * | 1979-07-03 | 1981-01-23 | Applic Mach Motrices | Distributeur hydraulique, destine notamment a equiper des servo-commandes d'avions et d'helicopteres |
US4976336A (en) * | 1988-09-13 | 1990-12-11 | Derlan Manufacturing Inc. | Lifting apparatus and lifting arm assembly for use therein |
JPH06270894A (ja) | 1993-03-16 | 1994-09-27 | Mitsubishi Heavy Ind Ltd | ヘリコプタのピッチコントロールロッド |
JP2758374B2 (ja) | 1995-02-28 | 1998-05-28 | 株式会社コミュータヘリコプタ先進技術研究所 | ヘリコプタロータの高調波制御装置 |
US5685141A (en) | 1995-12-26 | 1997-11-11 | General Electric Company | Lock for nozzle control in the event of hydraulic failure |
FR2747174B1 (fr) * | 1996-04-03 | 1998-07-10 | Samm Societe D Applic Des Mach | Distributeur hydraulique pour servocommandes d'aeronefs, notamment helicopteres |
DE19627869A1 (de) * | 1996-07-11 | 1998-01-15 | Zf Luftfahrttechnik Gmbh | Hubschrauber |
FR2765916B1 (fr) * | 1997-07-10 | 1999-08-20 | Hispano Suiza Sa | Inverseur de poussee a resistance amelioree aux impacts |
-
1999
- 1999-06-10 DE DE19926429A patent/DE19926429A1/de not_active Withdrawn
-
2000
- 2000-06-03 US US10/018,239 patent/US6676377B1/en not_active Expired - Fee Related
- 2000-06-03 EP EP00936856A patent/EP1185456B1/de not_active Expired - Lifetime
- 2000-06-03 WO PCT/EP2000/005070 patent/WO2000076844A1/de active IP Right Grant
- 2000-06-03 DE DE50005210T patent/DE50005210D1/de not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
---|
See references of WO0076844A1 * |
Also Published As
Publication number | Publication date |
---|---|
DE19926429A1 (de) | 2000-12-14 |
EP1185456B1 (de) | 2004-02-04 |
DE50005210D1 (de) | 2004-03-11 |
US6676377B1 (en) | 2004-01-13 |
WO2000076844A1 (de) | 2000-12-21 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE69300190T2 (de) | Einhakenvorrichtung, mit Befestigung der Fahrwerkeinfahrverriegelung eines Flugzeuges. | |
DE3213719C2 (de) | Vorrichtung zum Sperren der Drehbewegung einer Lenkspindel eines Kraftfahrzeugs | |
DE10125178B4 (de) | Individuelle Rotorblatt-Steuerungsvorrichtung | |
DE3331100A1 (de) | Stelleinrichtung fuer flugsteuerflaechen | |
DE3510957A1 (de) | Redundanz-servoantrieb, insbesondere fuer die betaetigung von flugsteuerungsorganen in flugzeugen | |
DE69904110T2 (de) | Elektromagnetische Betätigungseinrichtung mit Gewindespindelantrieb | |
DE2845788C2 (de) | ||
EP0343397A1 (de) | Redundante Antriebsvorrichtung | |
DE3236481A1 (de) | Betaetigungsvorrichtung zur umsetzung einer zweiachsen-schwenkbewegung in eine flaechenbewegung | |
DE1198159B (de) | Spindelantrieb mit auf der Spindel laufender Spindelmutter | |
DE69205810T2 (de) | Vorrichtung mit verminderter Störanfälligkeit zur Steuerung eines Hubschrauberrotors durch eine Taumelscheibe. | |
DE2018820A1 (de) | Verriegelungsvorrichtung an einem TeleskopausIe ger | |
EP0442265B1 (de) | Klemmvorrichtung für ein axial verschiebbares Stellglied zur Greiferumsteuerung an einem Greiferzylinder einer Bogenrotationsdruckmaschine | |
DE102019119657A1 (de) | Werkzeugwechsler für einen Roboter und Wechselsystem hierfür | |
DE1680046C3 (de) | Schaltvorrichtung für Wechselgetriebe von Kraftfahrzeugen | |
EP1185456B1 (de) | Einrichtung zum gleichzeitigen verriegeln mehrerer aktuatoren | |
DE2202006A1 (de) | Stellvorrichtung fuer ein Schiffsruderblatt | |
DE69003390T2 (de) | Feinregelungsvorrichtung der orientierung und/oder der lage einer nutzlast. | |
DE1576075B2 (de) | Parallelredundantes betaetigungssystem | |
DE2620742C2 (de) | Zentriereinrichtung für ein Schreibwerk mit einer Typenscheibe | |
DE3690115C2 (de) | Elektrischer Schalter mit Zwangsöffnung seiner Ruhekontakte | |
DE3409520C1 (de) | Vorrichtung zum Entriegeln gefalteter Stabilisierungsflossen oder -ruder von Flugkörpern | |
DE3236480A1 (de) | Steuerhebel-zentriervorrichtung | |
DE2744232C2 (de) | Handsteuereinrichtung zum Orientieren der Scheinwerfer eines Fahrzeuges | |
DE69300876T2 (de) | Doppelzylinderschloss. |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
17P | Request for examination filed |
Effective date: 20011030 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB IT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20040204 Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED. Effective date: 20040204 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20040217 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: GERMAN |
|
REF | Corresponds to: |
Ref document number: 50005210 Country of ref document: DE Date of ref document: 20040311 Kind code of ref document: P |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20040603 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FD4D |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20050101 |
|
26N | No opposition filed |
Effective date: 20041105 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20040603 |
|
EN | Fr: translation not filed |